Projectile launching



P 2 3951 B. CRAWLEY 2,549,778

PROJECTILE LAUNCHING Filed Dec. 14, 1945 2 Sheets-Sheet 1 n w end r01E'JlicK Er awle %2/ emzwmv mm W5 April 24, 1951 a. CRAWLEY PROJECTILELAUNCHING 2 Sheets-Sheet 2 Filed Dec. 14, 1945 Elick'. Draw lg PatentedApr. 24, 1951 UNITED STTS 2,549,778 Fries (Granted under the act ofMarch 3, 1883, as amended April 30, 1928; 370 0. G. 757) 2 Claims.

The invention described herein may be manufactured and used by or forthe Government for governmental purposes, without the payment to me ofany royalty thereon.

This invention relates to a means for mounting a projectile on alauncher to assure that the projectile is released therefrominstantaneously upon the commencement of its intended flight.

Methods have heretofore been practiced for launching fin-stabilized ornon-spinning projec tiles with instantaneous release. However, none ofthese methods are adaptable for launching spin-stabilized or spinningprojectiles because the projectile would have an erratic andunpredictable flight due to lack of balance about its longitudinal axis.

The principal object of the present invention is the provision of meanson a spin-stabilized type of projectile for mounting the same on alauncher to assure of the projectile being instantaneously and uniformlyreleased therefrom upon starting its intended flight.

Another object of the provision of a novel and relatively simpleconnecting means on a spinstabilized type of rocket projectile forreadily mounting the same on a launcher so that upon beinginstantaneously released therefrom a true and accurate flight of theprojectile will be as sured.

These and other objects and advantages will be apparent as thespecification isconsidered with the accompanying drawings wherein:

Figure l is a side elevation partly in section of a rocket provided withthe grooved rings;

Figure 2 is a sectional view of the same;

Figure 3 is a perspective view of a launching rack to be used inconjunction with the rocket;

Figure 4 is a perspective view of the rocket positioned on the launchingrack ready for firing;

Figures 5, 6, '7 and 8 are modified forms of holding brackets forholding the rocket on the launching rack;

' Figure 9 is a side view, partly in section, show: ing a method ofsupporting a rocket with a modified form of bracket;

Figure 10 is a similar view of the rear portion of a rocket providedwith a groove therein;

Figure 11 is a rear view of a rocket shown in Figure 10;

Figure 12 is a side elevation of a rocket having 4 solid bands providedthereon;

Figure 13 is a longitudinal section of a launching rack to be used inlaunching a rocket as shown in Figure 12;

Figure 14 is a section taken on lines i k-hi of a parts throughout theseveral views, numeral-l designates a conventional rocket projectileconsisting of a tubular body 2 and a curved cgive or head 3. The rocketprojectile is preferably of the spin-stabilized type which when launchedfrom a launcher will spin or rotate significantly about its longitudinalaxis during flight. While the means for effecting such a spinning actiondoes not constitute a part of this invention, it will be understood thatthis may be accomplished by arranging a series of spaced angularlydisposed openings, not shown, in the base plate closing the rear end ofthe projectile. Thus, when the projectile is fired by any suitableinitiating mechanism, not shown, the gases resulting from the burning ofthe projectile in the body of the projectile will be ejected through theangulariy dis posed openings and will impart a spinning action to theprojectile, in an obvious manner.

In order to enable the rocket projectile to be mounted on a launchingmechanism, coupling or .connecting means are arranged on the body of theprojectile. In the preferred form of my invention, two annular rings 4and 5 of some suitable material such as metal or plastic are fitted onthe projectile in spaced relationship adjacent the ogive 3 and rear endof the tubular body.

The forward ring 4, as best shown in Figure 1, is formed with arelatively flat annular inner face 6 substantially equal in diameter tothe diameter of the projectile so that when the ring is positionedthereon the flat face 6 will tightly seat and remain on the projectileduring its initial flight. The outer face of the ring is curved upwardlyand rearwardly, as at l, terminating in a relatively flat rear verticalwall 8. Formed in the rear wall 8 is a relatively shallow annular groove9.

The rearward ring 5 is formed with a relatively narrow fiat inner faceit! substantially equal in diameter to the diameter of the projectile toassure of the ring being tightly seated and remaining on the projectileduring its initial flight. The ring being formed with an upwardly andrear-- wardly curved outer face I l and the rear wall l2 thereof is cutaway to form a relatively shallow annular groove l3.

The rocket projectile I is preferably mounted for launching on anysuitable launching frame having latching clips or release devicesthereon for interengaging with the grooves 9 and IS in the respectiveprojectile rings 4 and 5. While it is to be understood that the launchermay be of any suitable construction and may be of the stationary typefor ground firing or may be mounted on aircraft, for the purpose ofillustration I have shown a rectangular frame structure in Figures 3 and4 consisting of side and end wires Hi and I5 and front and rear legs orstandards l5. The legs are preferably adjustable by any suitable meansnot shown, to permit the launcher being elevated or depressed for aimingpurposes in an obvious manner.

A pair of spaced downwardly depending latching clips or release hooks lare formed on a longitudinally extending centrally disposed wire i8secured to the end wires 15, The lower ends of the hooks I! are bentforwardly to provide relatively short extensions !9 which are adapted tofit within the grooves 9 and it of the rocket prcjectile rings 4 and 5and serve to support the pro jectile on the launcher. Thus when theprojectile is ignited and fired from the launcher, by an initiatingmechanism now shown, the projectile will be moved forwardly, relative tothe launcher, and the grooves in the rings will be relatively ininstantaneously removed out of engagement with the extensions E9 on thelatching clips ll and freed from the launcher. To assure of theprojectile clearing and being properly released from the launcher, it isessential that the rear ring 5 on the projectile be of smaller outsidediameter than the forward ring t so that, upon launching, the rear ring5 will be free to pass beneath the forward latching clip ll during theforward travel of the projectile. If the inner face of groove 9 onforward ring 4 is thus placed at a greater distance from the center lineof the rocket than the outer face i l of the rearward ring there will besufiicient clearance between the outer face ii of the rearward ring 5and the extension iii of the latching clip ll normally engaging groove 9of the forward ring 4 to permit free forward travel 1 of the rocket whenit is launched. In other words, the relative diameters of the rings aresuch that the forward latching clip will not impede the forward progressof the projectile during launching. As the rings are formed with curvedsymmetrical outer walls and are only of suificient size to accommodatethe latching clip extension receiving grooves, it will be apparent thatthe rocket projectile will be uniformly balanced and the rings will notinterfere with the ballistic eficiency of the projectile.

It will be understood that the latching clips may be provided with anysuitable retaining or locking means, not shown, for retaining the projectile in position and preventing the latter from slipping or otherwisebeing dislodged from the launcher.

An embodiment of the preferred form of projectile coupling or connectingmeans is illustrated in Figure 10 wherein an annular groove 2: is formedin the end wall of the projectile i. The groove 2! is of sufiicientdepth and size to accom-- modate the extension I!) of the rearwardlatching clip I! of the launcher. In this embodiment, it will beunderstood that the groove is substituted for the rearward annularprojectile ring 5 and that the annular grooved ring 4 will still bemounted on the projectile. The rearward clip I! is somewhat greater inlength than the forward clip so that when the forward clip 11 fitswithin the groove 9 in the ring 4, the groove 2| will receive theextension on the rearward clip so that the projectile will be supportedin an obvious manner on the launcher.

While I have illustrated and described a launcher frame havingdownwardly depending latching clips, it should be understood that therocket projectile may be supported on a launcher, such as thatillustrated in Figures 13 and 14, hav-- ing two spaced upstandingbrackets 22. Suitably mounted on the upper ends of the brackets aresubstantially L-shaped latching clips 23 having arcuately-shapedforwardly extending lips 24 formed thereon as best shown in Figure 14.The lips 24 are of sufficient length to accommodate the lower portionsof a pair of spaced annular rings 26 mounted on a rocket projectile 25,which rings 26 are formed with curved symmetrical outer walls 2? andflat rear walls 28. Thus, the rocket projectile is supported on thelauncher in ,an obvious manner. In this embodiment, it may also bedesirable to omit the rearward ring 26 from the projectile and soarrange the rear launcher bracket 22 that the latching clip 2% thereonwill engage with and support the rear end of the projectile, asillustrated in Figure 16.

It is to be understood that while I have shown a preferred form and twomodifications of my connecting means on a spin-stabilized type of rocketprojectile and launching apparatus for supporting the same to assure ofthe projectile being instantaneously released from the launcher, variousother changes and modifications may be made without departing from thescope and spirit of the appended claims. Thus, for example, thelatching. clips may constitute a continuous metal ring 38, as shown inFigure 8, which will interfit with the grooves 9 and I3 in the front andrear rings 4 and 5, or in lieu of this structure, a latching ring 3|illustrated in Figure 7 may be formed with a series of three spacedannular lips or segments 32 adapted to fit with the grooves of theprojectile rings. If desired, the structure of Figure 7 may be furthermodified to the form shown in Figure 5, wherein a latching ring 35 isprovided with a series of three uniformly spaced clips 34 which engagewith the grooves of the rings. A still further modification isillustrated in Figure 6 wherein the latching member 35 comprises aconvex tongue or lip 36 adaptable for fitting within the respectiveprojectile ring grooves.

What I claim is:

1. In combination with a rocket launching apparatus including a frame, acylindrical pointed rocket projectile, an annular ring encircling saidprojectile, a rearwardly directed recess in said ring, and a forwardlydirected latching 'clip formed on said frame, said clip having anextension thereon for interengaging with the recess in said ring forsupporting the projectile on said launching apparatus without hindranceto forward motion of said projectile upon firing of said rocket.

2. In combination with a rocket launching apparatus including a frame, acylindrical pointed projectile, spaced rings encircling said projectilerearwardly directed, annular grooves formed in said rings, and spacedlatching clips formed on said frame, said clips having bent extensionsthereon interfitting with the annular grooves in said rings forsupporting the projectile on said launching apparatus without hindranceto forward movement of said projectile on firing of said rocket.

BLICK CRAWLEY.

REFERENCES CITED The following references are of record in the file ofthis patent:

France Sept. 2, 1930

